Removal of components from aircraft

ABSTRACT

A method of removing a component from an aircraft includes attaching a device comprising a guide member to the aircraft; attaching the component (such as an actuator) to the guide member; detaching the component from the rest of the aircraft; and moving the guide member so that the component follows a predefined path of removal of the component. A device for use in such a method is also described.

RELATED APPLICATIONS

The present application is a divisional of U.S. application Ser. No.11/462,176 filed Aug. 3, 2006, which claims priority from, UK PatentApplication Number 0516066.8 filed Aug. 4, 2005, the disclosures ofwhich are hereby incorporated by reference herein in their entirety.

BACKGROUND

The present invention relates to a device for and method of removing acomponent (in particular, but not exclusively, actuators) from anaircraft.

The removal of components, in particular actuators, from aircraft(especially large aircraft) may be a difficult process. Many actuatorsused on large, modern aircraft (such as those that can function usingboth electrical and hydraulic power) are heavy (up to about 52 kg). Themanual handling of such heavy actuators may risk damage to the aircraftor the actuator or injury to the personnel handling the actuator.Moreover, Health and Safety legislation in the UK at least does notpermit removal of such actuators by hand, the use of a lifting devicesuch as a winch being necessary. In some cases, a winch can readily beused to remove an actuator from an aircraft when the actuator isaccessible from above; in such cases a portion of aircraft skin or panelcan be removed from an upper surface of the aircraft wing, the winchthen being used to raise the actuator above the wing before lowering itto the ground. The removal of an actuator from a wing by means of awinch is not however always practical, because there may be othercomponents or structures obstructing access to and removal of thecomponent by means of a winch.

Furthermore, with modern advances in aircraft wing design there is oftenlittle free space around the actuator. The removal of actuators and thelike from aircraft can thus be difficult in view of there being littleroom to manoeuvre the component during its removal. The lack of freespace can also result in there being no straightforward path of removalof the component from the aircraft.

The removal of components from large aircraft with relatively thin wingsis particularly problematic because the space provided to accommodatethe component is relatively small and the components are relativelylarge and heavy.

SUMMARY

The method and device of the present invention seek to mitigate at leastsome of the above-mentioned problems.

In accordance with a first aspect of the present invention, there isprovided a device for facilitating the removal of a component from anaircraft, the device comprising:

an attachment portion for attaching the device to the aircraft; and

a guide member comprising a support portion for receipt of thecomponent;

the guide member being so mounted that, when the device is used toremove a component from an aircraft with the component being supportedby the support portion, the support portion moves away from the aircraftalong a predefined path.

Such a device allows a component to be removed from an aircraft withoutrisk of the component straying from a predefined path (typically asingle path). Because the component does not stray from the predefinedpath, there is minimal or no risk of the removal of the componentcausing damage to the component, the rest of the aircraft or thepersonnel removing the component from the aircraft. This may becontrasted to the use of hoists or the removal of components by manualhandling where the path of removal is not predefined, there beingsubstantial risk of causing damage to the component, the rest of theaircraft and/or the personnel removing the component.

It is preferred that the device comprises a handle or handles forassisting in the movement of the guide member.

It is preferred that the guide member is pivotally mounted to allow, inuse, the support portion to be movable away from the aircraft.

The device may comprise a plurality of, and preferably two, attachmentportions.

Each attachment portion may be provided by a mounting component, such asa bracket.

It is preferred that the mounting component is attachable to a rib ofthe aircraft (typically a rib in the wing or tail of the aircraft).

It is preferred that the mounting component is readily detachable fromthe guide member.

The device may be arranged such that the axis of rotation of the pivotalmount of the guide member is remote from the component to be removed.

It is preferred that the mounting component forms part of the pivotalmount for the guide member.

It is preferred that the device is provided with a locking mechanism forsecuring the guide member in position to receive the component from theaircraft. This may be achieved by co-operation between the guide memberand a mounting component, if present. For example, a bolt may extendthrough an aperture in the mounting component (typically a bracket) andinto the guide member, thus securing the guide member for receipt of thecomponent. The locking mechanism is preferably removable andreplaceable.

It is preferred that the pivotal mount is at or near one end of thedevice and the handle or handles are at or near the other end of thedevice.

It is further preferred that the device is arranged to operate as asecond order or second class lever. This refers to the load (thecomponent being removed from the aircraft) being located between thefulcrum (provided by the pivotal mount) and the effort (provided at thehandles).

It is preferred that the handle or handles is/are readily removable fromthe guide member. This facilitates easy storage of the device.

Alternatively or additionally, the handle or handles may be readilycollapsible. This further facilitates easy storage of the device.

The guide member may comprise a frame and plate arranged across saidframe. The plate may be in the form of sheet metal.

The guide member may be provided with one or more support members forsupporting the component. The support members are preferably arranged tocontact with the component. The length of one or more of the supportmembers may be fixed at one of a plurality of values. The support membermay comprise a cylindrical post or the like.

The device is preferably supplied with means for securing the componentto the device. This may take the form of a belt.

One or more of the support members may be provided with a means ofsecuring the component to the device. For example, a support member maybe provided with a clamp. This may be especially beneficial if thecomponent to be removed is an actuator having an actuating pin. In thiscase, the clamp may be secured around the actuating pin.

It is preferred that one or more of the support members projectssubstantially orthogonal to the plane generally defined by the guidemember.

It is preferred that the device comprises two handles, further preferredthat the handles extend substantially parallel to one another.

The device may comprise an adjuster for adjusting the position of theguide member along the pivotal axis. This permits the position of theguide member to be optimised for the receipt of a particular component.In the event that the device comprises two or more mounting components,then it is preferred that two or more of the mounting components areprovided with said adjusters. The adjuster may comprise a screw, therotation of which causes displacement of the guide member.

The device may further comprise a hoist support bar. It is preferredthat the hoist support bar is, in use, attachable above the guidemember. This allows a hoist to be supported above the component so thatthe component can be lowered safely to the ground.

In accordance with a second aspect of the present invention, there isprovided a kit for facilitating the removal of a component from anaircraft, the kit comprising:

a guide member comprising a support portion for receipt of thecomponent;

a set of one or more mounting components for attaching the guide memberto the aircraft; and

a handle or handles for assisting in the movement of the guide member;the guide member being arranged to be pivotally attached to the one ormore mounting components so that, when the kit is used to remove acomponent from an aircraft with the component being supported by thesupport portion, the support portion moves away in a pivoting motionfrom the aircraft along a predefined path.

Preferably the kit further comprises a handle, or handles, for assistingin the movement of the guide member.

The guide member may be pivotally attachable to the one or more mountingcomponents. This provides a simple and convenient mechanism for removinga component from the aircraft.

The kit may comprise a plurality of sets of one or more mountingcomponents. It is preferred that each set is associated with attachmentto a particular part of an aircraft (and thus associated with theremoval of a particular component).

The kit may further comprise a hoist and pulley arrangement.

The kit may further comprise a slide (for example, a set of rails) that,in use, allows the component to be lowered towards the ground.

There may be provided a storage container for the storage of the kit.

The kit may comprise those features described with reference to thedevice of the first aspect of the present invention.

In accordance with a third aspect of the present invention, there isprovided a method of removing a component from an aircraft to which itis attached, by means of the use of a device in accordance with thefirst aspect of the present invention. The method may comprise thefollowing steps:

-   -   (a) providing a device in accordance with the first aspect of        the present invention,    -   (b) removing an outer panel of the aircraft to provide access to        the component to be removed,    -   (c) attaching the device to the aircraft,    -   (d) attaching the component to be removed to the support portion        of the device,    -   (e) detaching the component from the aircraft, and    -   (f) moving the support portion and the component away from the        aircraft.

The device may have the features of the device of the first aspect ofthe present invention. For example, the device may be provided with oneor more mounting components that are detachable from the guide member.

In accordance with a fourth aspect of the present invention, there isprovided a method of removing an actuator from a wing or tail of anaircraft, the method comprising:

-   -   (a) removing a panel from the underside of the wing or tail,    -   (b) attaching a device for the removal of the actuator to the        wing or tail of the aircraft,    -   (c) attaching the actuator to a support portion of the device,    -   (d) detaching the actuator from the aircraft, and    -   (e) moving the support portion so as to lower the actuator.

In accordance with a fifth aspect of the present invention there isprovided a method of removing a component from an aircraft, the methodcomprising:

(a) attaching a device comprising a guide member to the aircraft;

(b) attaching the component to the guide member;

(c) detaching the component from the rest of the aircraft; and

(d) moving the guide member so that the component follows a predefinedpath of removal of the component.

The device may be in accordance with the first aspect of the presentinvention. For example, the guide member may be provided by the deviceof the first aspect of the present invention.

The device may comprise a guide member that is separable from one ormore mounting components which are attachable to the aircraft. Step (c)may comprise attaching the one or more mounting components to theaircraft and then attaching the guide member to the one or more mountingcomponents.

The moving of the guide member along the predefined path may be assistedby the weight of the component. This provides a convenient way ofremoving a component from an aircraft.

It is preferred that the moving of the guide member is effectedmanually.

It is preferred that the path of removal comprises an arc. This allows acomponent to be removed from an aircraft by merely moving part of theguide member about a pivot point. The centre of rotation of the arc maybe remote from the component to be removed. It will of course beappreciated that the predefined path of removal of the component may beany path sufficient to allow safe removal of the component. The path mayneed for example to comprise a plurality of sections representative ofdifferent movements. For example the path may comprise a linear sectionand a non-linear section.

It is preferred that an outer panel of the aircraft is removed prior toremoval of the component.

The method may comprise, prior to step (b), removing an outer panel ofthe aircraft to provide access to the component to be removed, andwherein step (d) comprises moving the support portion and the componentaway from the aircraft. It is preferred that the device is attached toone or more ribs of the aircraft.

The path of removal may be on the underside of the aircraft. Theinvention is of particular application when the component is initiallypositioned in a wing or tail of an aircraft. In this case, it ispreferable that the wing or tail includes an aileron or an elevator,which is moved to an elevated position prior to attaching the device tothe aircraft.

The method according to the fifth aspect may further comprise loweringthe component in a controlled manner after step (d), optionally usingone or both of a hoist or a slide arrangement.

It is preferred that the mass of the device is less than 25 kg. Thepresent invention is of particular application when the mass of thecomponent to be removed from the aircraft is more than 25 kg.

In accordance with a sixth aspect of the present invention, there isprovided a method of manufacturing a device for the removal of acomponent from an aircraft, the method comprising:

-   -   (a) identifying a path of removal of the component from the        aircraft;    -   (b) designing a device provided with a guide member arranged        such that when the component is attached to the guide member and        when the guide member is attached to the aircraft, the guide        member is arranged to move so that the component follows said        path of removal of the component;    -   (c) manufacturing the device in accordance with the design.

There may of course be more than one possible path of removal. In such acase the path of removal is preferably chosen so as to be relativelysimple compared to other possible paths.

It will of course be appreciated that features of one aspect of thepresent invention may be incorporated into another aspect of theinvention. The methods of the third, fifth and sixth aspects of thepresent invention are preferably used to remove actuators from aircraft,such as those actuators that are used to control the movements ofailerons, elevators, spoilers or rudders. For example, the pre-definedpath of removal of a rudder actuator from the tail of an aircraft mayinvolve a rotation of the actuator about a substantially vertical axisto move the actuator away from the tailfin. The pre-defined path may, inthis case, further comprise a rotation of the actuator about asubstantially horizontal axis. Such a movement may orient the actuatorsuch that a winch arrangement may be conveniently used to lower theactuator to the ground.

BRIEF DESCRIPTION OF THE DRAWINGS

An embodiment of the present invention is described by way of exampleonly with reference to the attached schematic drawings of which:

FIG. 1 is a perspective view of a device in accordance with theembodiment;

FIG. 2 is a perspective view of the two brackets used in the device ofFIG. 1 to attach the device to the aircraft;

FIG. 3 is a perspective view of the guide member used in the device ofFIG. 1;

FIG. 4 is a perspective view of part of the underside of an aircraftwing, the aileron having been moved to an elevated position and theunderwing access panels having been removed;

FIG. 5 is a perspective view of the underside of an aircraft wing asshown in FIG. 4, the attachment brackets of the device in accordancewith the embodiment having been attached to the aircraft;

FIG. 6 is a perspective view of the underside of the aircraft wing asshown in FIG. 5, the device in accordance with the embodiment beingattached to the actuator for removal of the actuator;

FIG. 7 is a perspective view of the underside of the aircraft wing asshown in FIG. 6 showing the lowering of the actuator out of the aircraftwing;

FIG. 8 is a perspective view of the underside of the aircraft wing asshown in FIG. 7, the actuator having been rotated by 90° relative to theground; and

FIG. 9 is a perspective view of the underside of the aircraft wing asshown in FIG. 8, the guide member having been removed, and a hoisthaving been erected to lower the actuator to the ground.

The reader should note that, in many of the drawings, certain parts havebeen omitted for the sake of clarity.

DETAILED DESCRIPTION OF EMBODIMENTS

FIG. 1 shows a device in accordance with a first embodiment of thepresent invention for facilitating the removal of a component from anaircraft. The device 1 comprises attachment portions in the form ofbrackets 2 a, 2 b for attaching the device to the aircraft and a guidemember 3 comprising a support portion 10 for receipt of the component,the guide member 3 being mounted (pivotally, in this case) to allow, inuse, the support portion to be movable away from the aircraft. Thedevice 1 is also provided with handles 4 for assisting in the movementof the guide member. The device of FIG. 1 is designed to removeactuators from aircraft, particularly those used to control the movementof the ailerons. The guide member 3 is in the form of plates 26 a, 26 barranged across a frame 3 a. This provides a guide member 3 that isstrong, yet light, which is obviously a benefit for the handler of thedevice and a benefit if the device is to be stored on an aircraft. Thedevice 1 in FIG. 1 is shown with the guide member 3 and handles 4 beingattached to the brackets 2 a, 2 b. Bolts 6 a, 6 b secure the guidemember 3 to the brackets 2 a, 2 b by extending through frame 3 a intoapertures 14 a, 14 b formed in brackets 2 a, 2 b respectively (see FIG.2) and, in use, secure the guide member in position to receive thecomponent from the aircraft. Bolts 7 a, 7 b extend through an endportion (not shown) of the guide member 3 into a respective adjuster 8a, 8 b. This arrangement allows the guide member 3 to pivotally moveabout the axis (shown as reference numeral 16 in FIGS. 2 and 3) providedby bolts 7 a, 7 b and adjusters 8 a, 8 b. Referring to FIG. 2, the bolts7 a, 7 b extend through apertures 13 a, 13 b respectively in brackets 2a, 2 b respectively. The adjusters permit the position of the guidemember to be altered along the direction of the pivotal axis 16. This isof particular benefit in the present case where the device is for theremoval of an actuator from an aircraft. This feature allows the deviceto be used to remove more than one type of actuator; the spacing betweenadjacent ribs on which the device is mounted is different for each typeof actuator and being able to adjust the position of the guide memberalong the pivotal axis allows the device to be used to remove differenttypes of actuator. Further referring to FIG. 2, each bracket 2 a, 2 b isprovided with two D-nose clamps 11 a, 11 b, and 12 a, 12 b respectivelyfor securing the respective bracket to the rib of an aircraft wing.

Different sets of brackets may be used to help remove similar componentsfrom different parts of the aircraft.

The guide member and handles arrangement is now further described withreference to FIG. 3. The handles 4 are readily removable from the guidemember 3. This facilitates ease of storage. The handles 4 are secured tothe frame 3 a of guide member 3 by bolts 25 a, 25 b extending throughapertures formed in handle clamps 24 a, 24 b and plates 26 a, 26 b.Guide member 3 is provided with first support member 22 and secondsupport member 23 which together are provided for supporting an actuatoronce the actuator has been detached from the aircraft. First supportmember 22 comprises a clamp 22 a for securing the device 1 to theactuating pin of an actuator and an extendible post that allows theclamp 22 a to be moved to a suitable position so as to clamp theactuating pin.

The operation of the device of FIG. 1 in a method in accordance with thepresent embodiment is now described with reference to FIGS. 4 to 9illustrating the removal of an actuator from an aircraft.

An aileron 30 is moved to an elevated position and one or more underwingpanels is removed from the aircraft, leaving the aircraft as shown inFIG. 4. With the aileron in an elevated position, the actuating pin 32 aof the actuator 32 is extended, facilitating simple clamping of theactuating pin 32 a as described in more detail below. Referring to FIG.5, the brackets 2 a, 2 b are attached to wing ribs 33 a, 33 brespectively using the D-nose clamps 11 a, 11 b, 12 a, 12 b. Locatingblocks 15 a, 15 b as shown in FIG. 2 ensure that the brackets 2 a, 2 bare correctly fitted to ribs 33 a, 33 b. Referring to FIGS. 2, 3, 5 and6, the guide member 3 and handles 4 are then fitted onto the aircraftusing brackets 2 a, 2 b. Briefly, bolts 7 a, 7 b are inserted throughapertures 13 a, 13 b respectively, through end portions of frame 3 a,into adjusters 8 a, 8 b respectively. This effectively pivotally mountsthe guide member 3, with pivotal motion being permitted about axis 16.Adjusters 8 a, 8 b may then be adjusted so as to move the guide member 3in a direction parallel to the axis 16, allowing the position of firstsupport member 22 to be varied in the same direction so that theactuating pin 32 a may be secured by clamp 22 a. The user then uses thehandles 4 to swing the guide member up to the position shown in FIG. 6.Bolts 6 a, 6 b secure the guide member 3 to the brackets 2 a, 2 b byextending through frame 3 a into apertures 14 a, 14 b formed in brackets2 a, 2 b respectively (see FIG. 2). This secures the guide member 3 inposition to receive the actuator from the aircraft. The length ofextendible post 22 b may be varied so that clamp 22 a may be securedaround the actuating pin 32 a of the actuator 32. The extendible post 22b may be retracted to allow the position of the guide member 3 along theaxis 16 to be adjusted so that when the post 22 b is extended, the clamp22 a secures around the actuating pin 32 a. Second support member 23supports the actuator towards its rear. A belt 9 shown in FIG. 1 is tiedaround the actuator to provide additional support when the actuator isreleased from the aircraft and rotated down.

The actuator 32 is then detached from the aircraft by, inter alia,removing the locking pin (not shown) that secures the head 32 b of theactuating pin 32 a to the actuator connection plate 31.

Bolts 6 a, 6 b are then removed, thus allowing the guide member to moveabout pivot axis 16 as shown in FIG. 7 to a position as shown in FIG. 8.Thus the guide member moves in a predetermined manner so that theactuator follows a predefined path of removal from the aircraft.

In this position, the additional support provided by the belt 9 helpsprevent the actuator 32 from falling away from the device. FIG. 8 alsoshows a lifting eye 34 attached to the rear of the actuator.

FIG. 9 shows how a conventional hoist may be arranged to lower theactuator onto the ground or onto another suitable surface (e.g. aflat-bed trolley used to transport the actuator). A hoist support bar 5is fixed onto brackets 2 a, 2 b and a hoist 35 is then attached to thehoist support bar 5. A lifting eye clamp 36 is placed over lifting eye34, with a bar (not shown) extending through the lifting eye 34 toprevent the actuator from falling to the ground. The lifting eye clamp36 is connected to the hoist 35 with a rope (not shown). The guidemember 3 and handles 4 arrangement are then detached from the actuatorand optionally detached from brackets 2 a, 2 b. The hoist 35 is thenused to lower the actuator to the ground in a controlled manner.

Those skilled in the art will realise that the device of the presentinvention allows a user to remove components from aircraft safely, withlittle risk of damage to the component or the rest of the aircraft. Thisis possible because the device is designed and arranged so that thecomponent follows a predefined (and safe) path when being removed fromthe aircraft. In designing the device, firstly, a path of removal of thecomponent (in this case, the actuator) from the aircraft is determined.This path is advantageously chosen so that there is no or minimal damageto either the aircraft or the actuator on removal of the actuator. Sucha path of removal may be complex. In the present case, the path ofremoval of the actuator involves a movement away from the aileron 30along a circular arc, the centre of the arc being located below theactuator and therefore remote from the actuator and aircraft. A guidemember 3 is then designed, such that when the actuator 32 is attached tothe guide member and when the guide member is attached to the aircraft,the guide member is movable so that the component follows the desiredpath of removal of the component. The movement in an arc is created byproviding a guide member that is pivotally mounted at the relevantcentre of rotation. Once the guide member 3 has been designed andmanufactured, it may be used to remove the actuator from the aircraftalong the predefined path of removal.

Whilst the present invention has been described and illustrated withreference to a particular embodiment, it will be appreciated by those ofordinary skill in the art that the invention lends itself to manydifferent variations not specifically illustrated herein. For thatreason, reference should be made to the claims for determining the truescope of the present invention. By way of example, certain variations tothe above-described embodiments will now be described.

The device and method of the present invention may be used to removeother components from an aircraft, and from other parts of the aircraft(such as from the tail). For example, an actuator may be readily removedfrom the tail of an aircraft, the elevators being raised to allow accessto the actuator in the tail.

The device may further be provided with a slide (optionally replacingthe hoist arrangement). Considering FIG. 8, actuator 32 would be loweredusing the guide member 3 onto a slide, optionally formed by twosubstantially parallel rails. The actuator would be detached from thefirst support member 22 so that the actuator would either be allowed toslide freely down the slide or the slide would be controlled by a hoistarrangement. Such a slide would optionally allow the speed of thedescent of the actuator to be controlled.

Where in the foregoing description, integers or elements are mentionedwhich have known, obvious or foreseeable equivalents, then suchequivalents are herein incorporated as if individually set forth.Reference should be made to the claims for determining the true scope ofthe present invention, which should be construed so as to encompass anysuch equivalents. It will also be appreciated by the reader thatintegers or features of the invention that are described as preferable,advantageous, convenient or the like are optional and do not limit thescope of the independent claims.

The invention claimed is:
 1. A method of removing a component from anaircraft in which the component is installed, the method comprising: (a)attaching a device comprising a guide member to the aircraft in whichthe component is installed, the guide member being pivotally mounted forrotational motion about a pivot point; (b) attaching the installedcomponent to the guide member; (c) detaching the component from the restof the aircraft; and (d) rotating the guide member about the pivot pointthereby moving the guide member and the component away from theaircraft, said rotation of the guide member about the pivot point movingthe component along a predefined path of removal assisted by the weightof the component.
 2. A method according to claim 1, wherein the devicecomprises a handle operatively associated with the guide member and thehandle is used to rotate the guide member about the pivot point.
 3. Amethod according to claim 1, wherein the pivot point is remote from thecomponent to be removed.
 4. A method according to claim 1, wherein thepath of removal is on the underside of the aircraft.
 5. A methodaccording to claim 1, wherein, prior to the detaching step, thecomponent is above the pivot point.
 6. A method according to claim 1,wherein the component is initially positioned in the wing or tail of theaircraft.
 7. A method according to claim 1, wherein the mass of thecomponent is more than 25 kg.
 8. A method according to claim 1, whereinthe device comprises a guide member that is separable from one or moremounting components which are attachable to the aircraft, and whereinstep (c) comprises attaching the one or more mounting components to theaircraft and then attaching the guide member to the one or more mountingcomponents.
 9. A method according to claim 1, the device comprising asupport portion for supporting the component, wherein prior to step (b),removing an outer panel of the aircraft to provide access to thecomponent to be removed, wherein step (d) comprises moving the supportportion and the component away from the aircraft.
 10. A method accordingto claim 9, wherein the component is an actuator attached to a wing ortail of the aircraft, and the outer panel is removed from the undersideof the wing or tail.
 11. A method according to claim 1, wherein theaircraft has one or more ribs and the device is attached to said one ormore ribs of the aircraft.
 12. A method according to claim 6, whereinthe wing or tail includes an aileron or an elevator, the aileron orelevator being moved to an elevated position prior to attaching thedevice to the aircraft.
 13. A method of removing a component from anaircraft using a device which includes a mounting member providing anattachment portion for attaching the device to the aircraft; a guidemember comprising a support portion for receipt of the component to beremoved, the guide member being pivotally mounted to the mounting memberso that, when the component is being supported by the support portion inuse, the support portion moves pivotally away from the aircraft along apredefined path; and a handle operatively associated with the guidemember for assisting in the pivotal movement of the guide member; saidmethod comprising: attaching the attachment portion of the mountingmember of the device to the aircraft; attaching the component to thesupport portion of the guide member of the device; detaching thecomponent from the rest of the aircraft; and using a handle operativelyassociated with the guide member, moving the guide member about a pivotpoint, at which the guide member is pivotally mounted to the mountingmember, so that the component moves pivotally away from the aircraftalong a predefined path, wherein the moving of the guide member alongthe predefined path is assisted by the weight of the component.
 14. Amethod according to claim 13, wherein the moving of the guide member iseffected manually.
 15. A method according to claim 13, wherein the pathof removal is on the underside of the aircraft.
 16. A method accordingto claim 13, wherein, prior to the detaching step, the component isabove the pivot point.
 17. A method according to claim 13, furthercomprising before said attaching the component to the support portion ofthe guide member of the device, removing an outer panel of the aircraftto provide access to the component to be removed.
 18. A method accordingto claim 17, wherein the component to be removed is an actuator attachedto a wing or tail of the aircraft, and the outer panel is removed fromthe underside of the wing or tail.
 19. A method according to claim 18,wherein the wing or tail includes an aileron or an elevator, the aileronor elevator being moved to an elevated position prior to attaching thedevice to the aircraft.
 20. A method according to claim 13, wherein theaircraft has one or more ribs and the device is attached to said one ormore ribs of the aircraft.